EP2285682A2 - Zwischen einer antriebseinheit und einem lufteinlass einer flugzeugtriebswerksgondel eingesetzter messgeräteträger - Google Patents

Zwischen einer antriebseinheit und einem lufteinlass einer flugzeugtriebswerksgondel eingesetzter messgeräteträger

Info

Publication number
EP2285682A2
EP2285682A2 EP09772691A EP09772691A EP2285682A2 EP 2285682 A2 EP2285682 A2 EP 2285682A2 EP 09772691 A EP09772691 A EP 09772691A EP 09772691 A EP09772691 A EP 09772691A EP 2285682 A2 EP2285682 A2 EP 2285682A2
Authority
EP
European Patent Office
Prior art keywords
support
aircraft nacelle
air inlet
aerodynamic
aerodynamic surface
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Granted
Application number
EP09772691A
Other languages
English (en)
French (fr)
Other versions
EP2285682B1 (de
Inventor
Frédéric CHELIN
Cédric LECONTE
Fabienne Montetagaud
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Airbus Operations SAS
Original Assignee
Airbus Operations SAS
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Airbus Operations SAS filed Critical Airbus Operations SAS
Publication of EP2285682A2 publication Critical patent/EP2285682A2/de
Application granted granted Critical
Publication of EP2285682B1 publication Critical patent/EP2285682B1/de
Active legal-status Critical Current
Anticipated expiration legal-status Critical

Links

Classifications

    • A—HUMAN NECESSITIES
    • A23—FOODS OR FOODSTUFFS; TREATMENT THEREOF, NOT COVERED BY OTHER CLASSES
    • A23G—COCOA; COCOA PRODUCTS, e.g. CHOCOLATE; SUBSTITUTES FOR COCOA OR COCOA PRODUCTS; CONFECTIONERY; CHEWING GUM; ICE-CREAM; PREPARATION THEREOF
    • A23G9/00—Frozen sweets, e.g. ice confectionery, ice-cream; Mixtures therefor
    • A23G9/44—Frozen sweets, e.g. ice confectionery, ice-cream; Mixtures therefor characterised by shape, structure or physical form
    • A23G9/46—Aerated, foamed, cellular or porous products
    • A—HUMAN NECESSITIES
    • A23—FOODS OR FOODSTUFFS; TREATMENT THEREOF, NOT COVERED BY OTHER CLASSES
    • A23G—COCOA; COCOA PRODUCTS, e.g. CHOCOLATE; SUBSTITUTES FOR COCOA OR COCOA PRODUCTS; CONFECTIONERY; CHEWING GUM; ICE-CREAM; PREPARATION THEREOF
    • A23G1/00—Cocoa; Cocoa products, e.g. chocolate; Substitutes therefor
    • A23G1/0003—Processes of manufacture not relating to composition or compounding ingredients
    • A23G1/0026—Mixing; Roller milling for preparing chocolate
    • A23G1/003—Mixing; Roller milling for preparing chocolate with introduction or production of gas, or under vacuum; Whipping; Manufacture of cellular mass
    • A—HUMAN NECESSITIES
    • A23—FOODS OR FOODSTUFFS; TREATMENT THEREOF, NOT COVERED BY OTHER CLASSES
    • A23G—COCOA; COCOA PRODUCTS, e.g. CHOCOLATE; SUBSTITUTES FOR COCOA OR COCOA PRODUCTS; CONFECTIONERY; CHEWING GUM; ICE-CREAM; PREPARATION THEREOF
    • A23G3/00—Sweetmeats; Confectionery; Marzipan; Coated or filled products
    • A23G3/0002—Processes of manufacture not relating to composition and compounding ingredients
    • A23G3/0004—Processes specially adapted for manufacture or treatment of sweetmeats or confectionery
    • A23G3/0006—Manufacture or treatment of liquids, pastes, creams, granules, shred or powder
    • A23G3/001—Mixing, kneading processes
    • A23G3/0012—Mixing, kneading processes with introduction or production of gas or under vacuum; Whipping; Manufacture of cellular mass
    • A—HUMAN NECESSITIES
    • A23—FOODS OR FOODSTUFFS; TREATMENT THEREOF, NOT COVERED BY OTHER CLASSES
    • A23G—COCOA; COCOA PRODUCTS, e.g. CHOCOLATE; SUBSTITUTES FOR COCOA OR COCOA PRODUCTS; CONFECTIONERY; CHEWING GUM; ICE-CREAM; PREPARATION THEREOF
    • A23G9/00—Frozen sweets, e.g. ice confectionery, ice-cream; Mixtures therefor
    • A23G9/04—Production of frozen sweets, e.g. ice-cream
    • A23G9/20—Production of frozen sweets, e.g. ice-cream the products being mixed with gas, e.g. soft-ice
    • A—HUMAN NECESSITIES
    • A23—FOODS OR FOODSTUFFS; TREATMENT THEREOF, NOT COVERED BY OTHER CLASSES
    • A23P—SHAPING OR WORKING OF FOODSTUFFS, NOT FULLY COVERED BY A SINGLE OTHER SUBCLASS
    • A23P30/00—Shaping or working of foodstuffs characterised by the process or apparatus
    • A23P30/40—Foaming or whipping
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D33/00—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for
    • B64D33/02—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
    • B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
    • B64F5/40—Maintaining or repairing aircraft
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
    • B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
    • B64F5/60—Testing or inspecting aircraft components or systems
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D33/00—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for
    • B64D33/02—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes
    • B64D2033/0206—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes comprising noise reduction means, e.g. acoustic liners
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D33/00—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for
    • B64D33/02—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes
    • B64D2033/0266—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes specially adapted for particular type of power plants
    • B64D2033/0286—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes specially adapted for particular type of power plants for turbofan engines

Definitions

  • the present invention relates to a measurement device support interposed between a motor and an air intake of an aircraft nacelle.
  • An aircraft propulsion unit comprises a nacelle in which is arranged in a substantially concentric engine connected via a mast to the rest of the aircraft.
  • the nacelle comprises at the front an air inlet 10 making it possible to channel an air flow in a motor 12, a first part of the incoming air flow, called primary flow, passing through the motorization to participate in the combustion, the second part of the air flow, called secondary flow, being driven by a fan and flowing in an annular conduit defined by the inner wall of the nacelle and the outer wall of the engine.
  • the air inlet 12 comprises a lip 14 whose surface in contact with the aerodynamic flows is extended inside the nacelle by an inner duct 16 of substantially circular sections and outside the nacelle by an outer wall 18 of substantially circular sections.
  • the air inlet 12 is connected to the actuator by flange type connecting means 20 comprising on the one hand at the end of the inner duct 16 an annular collar 22 providing a first bearing surface, and on the other hand, at the motorization an annular flange 24 providing a second bearing surface capable of bearing against the first, bolts 26, rivets or the like being distributed on the circumference of the flanges 22 and 24 to keep them pressed against each other and thus ensure the connection between the air inlet and the engine.
  • a coating 28 intended to absorb a part of the sound energy, especially using the principle of Helmholtz resonators. In order to optimize the acoustic treatment, this coating 28 must extend over the largest surface and generally extends from the flange 22 to the lip 14.
  • a coating for acoustic treatment 28 also called acoustic attenuation panel, comprises from outside to inside an acoustically resistive porous layer 30, at least one cellular structure 32 and a reflective or impermeable layer 34.
  • the acoustically resistive layer is a porous structure having a dissipative role, partially transforming the acoustic energy of the sound wave passing through it into heat. It includes so-called open areas capable of passing acoustic waves and other so-called closed or full not allowing sound waves to pass but designed to ensure the mechanical strength of said layer.
  • This acoustically resistive layer is characterized in particular by an open surface area which varies essentially according to the engine, the components constituting said layer.
  • the measuring devices perpendicular to the surface in contact with the air flow and hold them perfectly.
  • these measuring devices must not disturb the flow entering the engine, otherwise the noise emitted by said engine would be different, and must be placed flush with the surface in contact with the air flow.
  • the present invention aims to provide a support for at least one measuring device optimizing the measurement.
  • the invention relates to an aircraft nacelle comprising an air inlet for channeling an air flow towards a motor, said air inlet having an inner duct forming an aerodynamic surface in contact asec the air flow extended aft by an aerodynamic surface of a duct of the engine, characterized in that it comprises a support of at least one measuring device, said support, of annular shape, being adapted to be interposed removably between the air intake and the engine and having a so-called aerodynamic surface capable of ensuring the continuity of the aerodynamic surfaces disposed downstream and upstream in the direction of flow of the air flow.
  • FIG. 1 is a section along a radial plane of part of the front of an aircraft nacelle according to the prior art
  • FIG. 2 is a section along a radial plane of part of the front of an aircraft nacelle according to the invention
  • FIG. 3 is a section along a radial plane illustrating in detail a support of at least one measuring device interposed between an air inlet and an engine of an aircraft nacelle;
  • FIG. 4 is a perspective view of part of the support of FIG. 3
  • FIG. 5 is a perspective view of the support of FIG. 3
  • FIG. 6 is a perspective view illustrating in detail a support according to the invention and its connecting means to the air inlet and the motor, said support being equipped with measuring devices.
  • FIG. 2 shows a part of the front of a nacelle of an aircraft comprising at 40 an air inlet making it possible to channel an air flow 42 towards an engine 44.
  • longitudinal direction a direction parallel to the longitudinal axis of the engine.
  • the air inlet 40 comprises a lip 46 whose surface in contact with the incoming air flow 42 is extended inside the nacelle by an inner duct 48 of substantially circular sections and outside the nacelle by an outer wall 50 of substantially circular sections.
  • the inner duct 48 comprises an aerodynamic surface 52 in contact with the air flow 42 which extends towards the rear of the nacelle by an aerodynamic surface 54 of a duct 56 of the engine.
  • the inner duct 48 of the air inlet comprises at the rear a ring-shaped edge facing a ring-shaped edge of the duct 56 of the engine.
  • the inner duct 48 comprises an annular flange 58 comprising a first bearing surface forming the rear edge of said inner duct 48.
  • the duct 56 of the motorization comprises an annular flange 60 having a second bearing surface forming the front edge of said duct 56 substantially parallel to the first bearing surface.
  • the flanges 58 and 60 comprise orifices 62 capable of allowing the passage of rods, arranged facing each other, spaced apart and distributed around the circumference of the flanges.
  • the inner duct 48 comprises a coating for the acoustic treatment 64, also called acoustic attenuation panel, comprising from the outside to the inside an acoustically resistive porous layer, at least one cellular structure and a reflective or impermeable layer, the acoustically resistive layer forming the aerodynamic surface 52.
  • the engine, the air intake and the sound attenuation panel are not more detailed because they are known to those skilled in the art.
  • the nacelle comprises a support 66 of at least one measuring device 68, independent of the motorization and the air inlet.
  • This support 66 of annular shape as illustrated in Figure 5 comprises a so-called aerodynamic surface 70 capable of ensuring the continuity of the aerodynamic surfaces 52 and 54 arranged downstream and upstream in the direction of flow of the air flow 42.
  • This support can be made in one or more parts.
  • This arrangement makes it possible to limit the effects of the support on the air flow 42.
  • the support 66 comprises first connecting means for transmitting the forces between the air inlet 40 and said support 66 and second connection means for transmitting the forces between the motor 44 and said support 66
  • the connecting means connecting the support to the air inlet and to the motorization make it possible to make it removable.
  • the support 66 has suitable shapes.
  • the support 66 has a substantially constant section on its circumference, U-shaped, the base of the U forming the aerodynamic surface 70, the branches of the U forming bearing surfaces in front of a part of the back song of the air inlet and secondly of the song before the motorization.
  • one of the branches of the U of the support 66 forms an annular flange 72 comprising a bearing surface that can be pressed against the bearing surface of the annular flange 58 of the inner duct 48.
  • the first connecting means comprise bolts, rivets 74 or the like, distributed around the circumference of the support 66, to hold the flanges 58 and 72 pressed against each other and to ensure the transmission of the forces between the air inlet 40 and the support 66.
  • the other leg of the U of the support 66 forms an annular flange 76 having a bearing surface that can be pressed against the bearing surface of the annular collar 60 of the led 56 of the engine.
  • the second connecting means comprise bolts, rivets 78 or the like, distributed around the circumference of the support 66, to hold the flanges 60 and 76 pressed against each other and to ensure the transmission of forces between the motorization 44 and the support 66.
  • the support 66 may comprise at least one extension 80 increasing the surface area of the aerodynamic surface 70 so as to cover any recess 82 provided at the edge of the front edge. the motorization and / or the rear edge of the air inlet, as illustrated in FIG. 3.
  • the recess 82 serves for mounting the support 66, in particular by housing certain elements of the connection between the edge rear of the air inlet and the support 66, the extension 82 covering the fastening and the aerodynamic flow insulation to reduce disturbances.
  • the support 66 is instrumented with measuring devices 68.
  • microphones are distributed over the entire circumference.
  • a microphone has a cylindrical shape with a shoulder 84.
  • the base of the U of the support 66 comprises, for each microphone, a through hole 86 opening at the level of the aerodynamic surface 70.
  • the hole 86 comprises a countersink 88 whose diameter is adapted to that of the shoulder 84 of the microphone to be fixed.
  • each microphone is held in a hole 86 so as to be substantially perpendicular to the aerodynamic surface 70, its end being substantially flush with said surface 70 so as not to interfere with the air flow 42. inside or outside more than 0.1 mm will generate turbulence.
  • Each microphone 68 is fixed in the hole by any appropriate means, for example by gluing, screwing or the like.
  • the support 66 thus instrumented makes it possible to obtain an optimal measurement because the microphones 68 are placed perpendicularly and close to the surface in contact with the air flow 42, do not disturb the air flow and are perfectly maintained. Finally, the support 66 being removable, it can be removed from the nacelle after a measurement campaign, the air inlet is then secured directly to the engine.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Life Sciences & Earth Sciences (AREA)
  • Food Science & Technology (AREA)
  • Polymers & Plastics (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Manufacturing & Machinery (AREA)
  • Transportation (AREA)
  • Combustion & Propulsion (AREA)
  • Testing Of Engines (AREA)
  • Aerodynamic Tests, Hydrodynamic Tests, Wind Tunnels, And Water Tanks (AREA)
  • Motor Or Generator Frames (AREA)
  • Railway Tracks (AREA)
  • Measuring Fluid Pressure (AREA)
  • Wind Motors (AREA)
EP09772691A 2008-06-06 2009-06-03 Zwischen einer antriebseinheit und einem lufteinlass einer flugzeugtriebwerksgondel eingesetzter messgeräteträger Active EP2285682B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR0853759A FR2932160B1 (fr) 2008-06-06 2008-06-06 Support d'appareils de mesure intercale entre une motorisation et une entree d'air d'une nacelle d'aeronef
PCT/FR2009/051049 WO2010001009A2 (fr) 2008-06-06 2009-06-03 Support d'appareils de mesure intercale entre une motorisation et une entree d'air d'une nacelle d'aeronef

Publications (2)

Publication Number Publication Date
EP2285682A2 true EP2285682A2 (de) 2011-02-23
EP2285682B1 EP2285682B1 (de) 2012-04-25

Family

ID=40230013

Family Applications (1)

Application Number Title Priority Date Filing Date
EP09772691A Active EP2285682B1 (de) 2008-06-06 2009-06-03 Zwischen einer antriebseinheit und einem lufteinlass einer flugzeugtriebwerksgondel eingesetzter messgeräteträger

Country Status (6)

Country Link
US (1) US8757541B2 (de)
EP (1) EP2285682B1 (de)
CN (1) CN102056803B (de)
AT (1) ATE555018T1 (de)
FR (1) FR2932160B1 (de)
WO (1) WO2010001009A2 (de)

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FR2970753B1 (fr) * 2011-01-26 2015-01-16 Airbus Operations Sas Dispositif de liaison plus particulierement adapte pour assurer la liaison entre une entree d'air et une motorisation d'une nacelle d'aeronef
US9708072B2 (en) 2014-04-30 2017-07-18 The Boeing Company Aircraft engine nacelle bulkheads and methods of assembling the same
US9604438B2 (en) 2014-04-30 2017-03-28 The Boeing Company Methods and apparatus for noise attenuation in an engine nacelle
US9656761B2 (en) 2014-04-30 2017-05-23 The Boeing Company Lipskin for a nacelle and methods of making the same
US9938852B2 (en) 2014-04-30 2018-04-10 The Boeing Company Noise attenuating lipskin assembly and methods of assembling the same
BE1025077B1 (fr) * 2017-03-22 2018-10-23 Safran Aero Boosters S.A. Capot de turbomachine avec ecran
CN107738759B (zh) * 2017-11-13 2023-12-01 山东太古飞机工程有限公司 飞机发动机整流罩拆除及安装用加力器
CN112798560B (zh) * 2020-12-24 2023-05-23 中国航空工业集团公司西安飞机设计研究所 一种腔体内壁散射特性预估载体
FR3128444A1 (fr) 2021-10-26 2023-04-28 Airbus Operations (S.A.S.) Nacelle d’aéronef comprenant une liaison entre des conduits comportant des collerettes orientées vers l’intérieur et aéronef comprenant au moins une telle nacelle

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Also Published As

Publication number Publication date
WO2010001009A3 (fr) 2010-03-18
FR2932160B1 (fr) 2010-11-26
ATE555018T1 (de) 2012-05-15
US20110147534A1 (en) 2011-06-23
FR2932160A1 (fr) 2009-12-11
CN102056803A (zh) 2011-05-11
EP2285682B1 (de) 2012-04-25
WO2010001009A2 (fr) 2010-01-07
US8757541B2 (en) 2014-06-24
CN102056803B (zh) 2014-01-29

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